摘要
飞机使用环境谱的不断变化会对机体结构造成腐蚀损伤,工程上难以在外场环境下进行实时损伤检测与疲劳性能试验。点蚀作为腐蚀的初始阶段,危害性大,部位也难以预测。采用损伤力学和有限元相结合的方法,以材料疲劳S-N数据为基础,将点蚀损伤认为是一种初始缺陷,建立基于损伤力学假设的点蚀损伤疲劳寿命预估方法,并提出一种改进型损伤参数反演方法。对点蚀疲劳失效过程进行数值模拟,模拟结果与试验结果吻合,证明该方法应用于金属材料点蚀疲劳问题中是合理的、可行的,为后续实际预腐蚀损伤疲劳研究奠定了基础。
The continuous effects of aircraft operational environment spectrum will cause corrosion damage to aircraft structures, which is difficult to detect or test in outside field. Based on the material＇s S-N statistics and supposing the pitting-corrosion damage as the initial defect, a model to calculate the fatigue life of pitting-corro- sion damage by combining the damage mechanics with the finite element method is established, and an improved damage parameters determining method is proposed. By comparing the simulation results of pitting-corrosion damage with the test results, the method is proved to be accuracy and feasible in assessing metallic pitting-cot rosion damage and can be represented as references for further study in corrosion fatigue.
出处
《航空工程进展》
2014年第2期233-238,共6页
Advances in Aeronautical Science and Engineering
基金
国家自然科学基金(51174162)
关键词
损伤力学
点蚀
疲劳寿命
疲劳损伤演化
有限元
damage mechanics
pitting-corrosion
fatigue life
fatigue damage evolution
finite element
作者简介
通信作者：苟义龙（1988-），男，硕士研究生。主要研究方向：结构疲劳与断裂。363016071@qq．com
殷之平（1977-），男，副教授。主要研究方向：结构疲劳、断裂与可靠性。
黄其青（1955-），女，教授，博导。主要研究方向：结构疲劳、断裂与可靠性。
